Van's Aircraft G3X User manual

PAGE:REVISION:DATE:
VAN'S AIRCRAFT, INC.
42PiS-01RV-12iS001/19/19
PARTICIPANTS:
DATE OF COMPLETION:
(AV-532L CABLE)
AV-532L
VOR/LOC/GS ANTENNA
GMU 11
GARMIN
MAGNETOMETER
GSU 25
GARMIN AIR DATA
ATTITUDE HEADING
REFERENCE SYSTEM
GMA 245
GARMIN AUDIO PANEL
GTN 650
GARMIN GPS/NAV/COM
GEA 24
GARMIN ENGINE
INDICATION
SYSTEM
GA 36 OR GA 37
GARMIN GPS ANTENNA
F-00214
GARMIN AFT PITOT LINE F-00212
GARMIN AOA LINE
F-00216
GARMIN STATIC LINE
2X GDU 460
G3X TOUCH
FLIGHT DISPLAY
AV-60007
IGNITION
MODULE
GTX 35R
GARMIN TRANSPONDER SECTION 42PiS:
GARMIN G3X
NAV/COM SYSTEM
GMC 307
GARMIN CONTROL PANEL
GAD 29
GARMIN DATA
INTERFACE
ADAPTER

VAN'S AIRCRAFT, INC.
PAGE: REVISION: DATE: 01/19/190RV-12iS42PiS-02
NOTE: If the VS-1213 V-Stab Tip Fairing has already been riveted to the top of the V-Stab Assembly, it be will necessary to
drill out the rivets securing the fairing.
Step 1: Separate the F-00205 Nutplate Spacer
into the F-00205 Shim, K1000 Drill Temp, and
MS20151 Drill Temp by cutting along the lines
shown in Figure 1.
Step 2: Cleco the MS21051 Drill Temp to the
aft-most hole in the VS-1213. Match-drill #40 the
holes into the VS-1213 as shown in Figure 2.
Repeat for the opposite side.
Step 3: Cleco the K1000 Drill Temp to the
remaining #30 holes in the VS-1213, then
match-drill #40 the holes into the VS-1213 as
shown in Figure 2.
Repeat for the opposite side.
Step 4: Machine countersink (flush outside) all #40
holes just match-drilled into the VS-1213 for an
AN426AD3 rivet. See Figure 2.
Step 5: Final-drill #27, then machine-countersink all
#30 holes in the VS-1213. See Figure 2.
Step 6: Rivet the nutplates onto the inside of the VS-1213 as shown in Figure 2.
Step 7: Final-drill #27 all holes in the VS-1201 Main Skin which are above the VS-1205 Tip Rib. See Figure 3.
Step 8: Dimple all #27 holes for #6 screws as shown in Figure 3.
CUT
F-00205 SHIM
K1000 DRILL TEMP
MS21051 DRILL TEMP
(#30 HOLE
ON SIDE)
(#30 HOLE
CENTERED)
(#12 HOLE
CENTERED)
FIGURE 1: SEPARATING THE F-00205
FIGURE 2: FAIRING MODIFICATIONS
(FAIRING SHOWN UPSIDE DOWN)
K1000 DRILL TEMP
MS21051 DRILL TEMP
1/8 CLECO
1/8 CLECO
10X MATCH-DRILL #40
2X MATCH-DRILL #40
2X
10X
VS-1213
MACH CSK
ALL #40 HOLES
(FLUSH OUTSIDE)
FINAL DRILL #27 THEN
MACH CSK FOR #6 SCREW
(FLUSH OUTSIDE)
12X
VS-1201
VS-1205
FIGURE 3: VERTICAL STAB PREP
FINAL-DRILL #27
DIMPLE FOR #6 SCREW
(FLUSH OUTSIDE)
MS21051L06
2X AN426AD3-4
K1000-06
2X AN426AD3-4

42PiS-03RV-12iS001/19/19 PAGE:REVISION:DATE:
VAN'S AIRCRAFT, INC.
4X MATCH-DRILL #30
MARK VS-1205 THROUGH THESE HOLES.
VS-1201
VS-1205
FIGURE 1: DRILLING THE VS-1205
Step 1: Locate the F-00203 Nav Antenna Doubler on the VS-1205 as shown in Figure 1.
Step 2: Match-Drill #30 the forward and aft-most holes in the F-00203 into the web of the VS-1205. Cleco each hole before drilling
the next. See Figure 1.
Step 3: Use a permanent marker through the #27 holes in the F-00203 to mark the VS-1205 as shown in Figure 1.
Step 4: Remove the clecos and the F-00203 from the VS-1205.
Step 5: Drill #30 a hole near the aft two lightening holes in the VS-1205 as shown in Figure 1.
4X MACH CSK
(FLUSH THIS SIDE) 2X MS21051L3
2X AN426AD3-4
F-00203
F-00203 CLEARANCE FOR
NUTPLATES
UNDER F-00203
Step 6: Machine countersink the #40 holes in the F-00203 as shown in Figure 2.
Step 7: Rivet the nutplates to the bottom of the F-00203 as shown in Figure 2.
Step 8: Using the marks made in Step 3 as a starting point, trim away the inside edge of the lightening hole in the VS-1205 to clear
the nutplates installed under the F-00203. See the hatched area in Figure 2.
Thoroughly deburr these notches once they have reached final size.
Step 9: Rivet the F-00203 to the VS-1205 as shown in Figure 2.
Step 10: Cleco the K1000 Drill Temp to the #30 hole in the VS-1205
then match drill #40 the holes as shown in Figure 2.
Step 11: Remove the cleco and K1000 Drill Temp from the VS-1205,
then final drill the #30 hole in the VS-1205 to #12. See Figure 1.
Step 12: Machine countersink the #40 holes in the F-00205 Shim as shown in Figure 3.
Step 13: Fabricate the F-00206 AV-532 Spacer as
shown in Figure 4.
FIGURE 2: F-00203 NUTPLATE INSTALLATION
8X LP4-3
DRILL #30
MATCH-DRILL #40
K1000 DRILL TEMP
MACH CSK
FIGURE 3: F-00205 SHIM PREP
1.6 [40.6 mm]
UHMW-125X1X2 FIGURE 4: FABRICATING
THE F-00206
2X DRILL #11
F-00205 SHIM

VAN'S AIRCRAFT, INC.
PAGE: REVISION: DATE: 01/19/190RV-12iS42PiS-04
F-00206
AV-532L
ANTENNA
2X AN3-13A
MATCH DRILL #30
ES-00301
LP4-5
NAS1149FN432P
Step 1: Position the ES-00301 on the aft-most lightening hole as shown in Figure 1, then match-drill #30 the rivet hole into the
VS-1205.
Step 2: Rivet the ES-00301 to the VS-1205 with the hardware shown in Figure 1. A small dab of superglue can be used to hold the
washer to the bottom of the VS-1205 if necessary.
Step 3: Rivet the F-00205 Shim and the nutplate onto the VS-1205 as shown in Figure 1.
Step 4: Temporarily secure the F-00206 and AV-532L Antenna on to the VS-1205 with the fasteners shown in Figure 1.
Step 5: Mark the longitudinal position of the AV-532L Antenna elements on the VS-1201 as
shown in Figure 1.
Step 6: Measure the vertical height of the AV-532L Antenna element
above the top edge of the VS-1201 as shown in Figure 1 and record
the value.
Remove the AV-532L from the V-Stab Assembly.
Step 7: Temporarily install the VS-1213 onto the V-Stab
Assembly with #6 screws as shown in Figure 1.
Step 8: Transfer the positioning marks made in Step 5 from
the VS-1201 to the VS-1213.
Measure and mark the height of the AV-532L Antenna
element onto the VS-1213.
NOTE: The notch cut in Step 9 should be smoothly
radiused at the top (approx 1/8 in. [1.6 mm] radius).
Step 9: Remove the VS-1213 from the V-Stab
Assembly and cut a notch in the VS-1213 from the
antenna element positioning marks, down to the
lower edge of the VS-1213.
Ensure adequate clearance around the antenna
elements to allow for vibration of the elements
as shown in the Detail View in Figure 1.
F-00205 SHIM
2X CCR264SS-3-2
K1000-3
VS-1213
VS-1201
VS-1213
VS-1201
AV-532L
NOTCH FOR 1/32-1/16 [.8-1.6 mm]
CLEARANCE ALL SIDES
FIGURE 1: NOTCHING THE FAIRING
VS-1205

42PiS-05RV-12iS001/19/19 PAGE:REVISION:DATE:
VAN'S AIRCRAFT, INC.
PLASTIC TIE-WRAP 5.5"
2X PLASTIC TIE-WRAP 5.5"
F-00204
NAV ANTENNA CONDUIT
Step 1: Drill #19 a hole in the VS-1208 Rib at the location shown in Figure 1.
Step 2: Fabricate the F-00204 Nav Antenna Conduit by cutting a piece of NT Duct 5/8 to a length of of 44 1/2 in. [113 cm].
Step 3: Route the F-00204 through the aft-most set of lightening holes in the ribs of the V-Stab Assembly. See Figure 2.
Step 4: Secure the F-00204 to the ES-00301 on the top of the V-Stab Assembly.
The F-00204 should extend approximately 1/4 in. [6.4 mm] past the ES-00301. See Figure 2.
Step 5: Secure the bottom of the F-00204 to the VS-1208 using two crossing tie-wraps through the hole in the VS-1208 as
shown in Figure 2.
FIGURE 2: INSTALLING THE NAV ANTENNA CONDUIT
V-STAB ASSEMBLY
DRILL #19
5/8 [15.9 mm]
FROM EDGE
VS-1208
FIGURE 1: DRILLING THE V-STAB RIB
LEFT
UP
FWD

VAN'S AIRCRAFT, INC.
PAGE: REVISION: DATE: 01/19/190RV-12iS42PiS-06
PILOT DRILL #30
THEN STEP-DRILL 5/8
Step 1: Drill #30 a hole in the F-1278 Top Skin at the location shown in Figure 1.
Step 2: Use a step drill to enlarge the #30 hole in the F-1278 to 5/8.
Step 3: Install the snap bushing into the F-1278 as shown in Figure 1.
Step 4: Cut strips of MS21266 Grommet to the length shown in Figure 2 to fabricate 8 of the F-1257B Cable Anti-Chafe Strips.
F-1278
FIGURE 1: DRILLING THE TAILCONE
SB625-7
FIGURE 2: FABRICATING THE F-1257B
(QTY 8 REQD)
SCALE 1 TO 1
3 [76.2 mm]
MS21266

42PiS-07RV-12iS001/19/19 PAGE:REVISION:DATE:
VAN'S AIRCRAFT, INC.
AV-532L CABLE
F-1238-R
DRILL #30,
SECURE AV-532L CABLE
WITH PLASTIC TIE-WRAP 4"
F-1211A
APPROX.
1/2 [12.5 mm]
PLASTIC
TIE-WRAP 4"
F-1257B
F-1281-L
F-1281-R STIFFENER
Step 1: Drill #30 a hole in the center of the inboard flange of the F-1238-R as the location shown in Figure 1.
NOTE: When positioning and securing the AV-532L cable in the following steps, ensure that the AV-532L cable is not
rubbing on the sharp edge of of the F-1279-R Upper Right Skin stiffener, and is clear of all control cables.
Step 2: Route the AV-532L cable through the snap bushing in the F-1278.
Step 3: With the AV-532L cable extending outside the tailcone as shown, secure the AV-532L cable to the F-1238-R with a
tie-wrap. See Figure 1.
Step 4: Route the AV-532L cable from the F-1238-R to the stiffener of the F-1281-R Lower Skin. Cover the stiffener edge with a
F-1257B where the cable enters the stiffener.
Step 5: Secure the AV-532L cable and F-1257B to the stiffener of the F-1281-R with a tie-wrap
as shown in Figure 1.
FIGURE 1: SECURING THE AV-532L CABLE
54 [137.2 CM]
(PAST SURFACE OF F-1278)
F-1279-R STIFFENER

VAN'S AIRCRAFT, INC.
PAGE: REVISION: DATE: 01/19/190RV-12iS42PiS-08
AV-532L CABLE
F-1257B TYP.
F-1281-R STIFFENER
F-1209-R
FUSELAGE FRAME
F-00217
TYP.
PLASTIC
TIE-WRAP 4"
TYP.
DAB OF RTV OR
FUEL TANK
SEALANT
TYP.
Step 1: Route the AV-532L cable up the F-1281-R stiffener, passing through the lightening holes in each of each fuselage frame
as shown in Figure 1.
NOTE: Airframes with dual pass through holes in the F-01202B-1 should route the AV-532L cable through the foremost
hole.
Step 2: Following the path of the WH-00136 forward of the
F-01207C-L, route the AV-532L cable forward through the airframe
and up through the wire pass-through hole in the F-01202B-1 as
shown in Figure 1.
Step 3: Install the F-1257Bs onto the F-1281-R stiffener to
protect the AV-532L cable at all points where the cable
enters/exits the stiffener. See the Detail View of Figure 1.
Step 4: Cut 3 strips of MS21266 grommet to 4 3/8 in. [111.1mm] to fabricate the F-00217s.
Step 5: Install the F-00217s into the fuselage frames as shown in the Detail View of Figure 1.
Step 6: Once the entire AV-532L cable has been routed and positioned correctly, secure the
AV-532L cable to the F-1281-R stiffener with tie-wraps as shown.
FIGURE 1: ROUTING THE AV-532L CABLE
F-01202B-1
F-1207C-L
AV-532L CABLE
6 [152.4 mm]

42PiS-09RV-12iS001/19/19 PAGE:REVISION:DATE:
VAN'S AIRCRAFT, INC.
FIGURE 1: ROUTING THE AV-532L CABLE
THROUGH THE V-STAB ASSEMBLY
AV-532L NUT
AV-532L LOCK WASHER
MS21919DG6
AV-532L CABLE
F-00204
AN525-10R8
Step 1: Reinstall the V-Stab Assembly to the airframe, while simultaneously routing the AV-532L cable
through the F-00204. See Figure 1.
A piece of safety wire passed through the F-00204 prior to reassembly can be used to pull the
AV-532L cable up through the F-00204 if necessary.
Step 2: Connect the ring terminals on the end of the AV-532L cable onto the studs of the AV-532L
antenna with the included fasteners as shown in Figure 2.
Step 3: Clasp the cushion clamp over the AV-532L cable and secure the cushion clamp to t he F-00205
relieving any strain on the ring terminals. See Figure 2.
Step 4: Reinstall the VS-1213 onto the V-stab assembly as shown in Figure 3.
FIGURE 2: CONNECTING THE AV-532L CABLE
AV-532L ANTENNA
F-00205 VS-1213
12X AN507C632R6
V-STAB ASSEMBLY
V-STAB
ASSEMBLY
FIGURE 3: INSTALLING THE V-STAB FAIRING

VAN'S AIRCRAFT, INC.
PAGE: REVISION: DATE: 01/19/190RV-12iS42PiS-10
F PLASTIC TEE
F-00012
AFT PITOT LINE
F-00014
F-00012
AFT PITOT LINE
GMU 11
4X
AN526C632R8
AN960C6
MS21044C06
F-00142
4X
AN526C632R6
AN960C6
MS21044C06
F-00009-R
F-00009-L
NOTE: Never use magnetic tipped screwdrivers or
other magnetic objects when working with hardware
near the GMU 11. The GMU 11 is very sensitive and
may be influenced by any magnetized hardware.
Step 1: Install the GMU 11 to the F-00142 GMU 11 Attach
Plate as shown in Figure 1.
Step 2: Mount the F-00142 to the F-00009-L & -R ADAHRS
Brackets in the upper tailcone skins as shown in Figure 2.
Ensure the GMU 11 connector is facing aft.
Step 3: Connect the 9-pin d-sub connector labeled
"MAGNETOMETER" from the WH-00136 to the GMU 11.
F-000142
FIGURE 1: GMU 11 INSTALLATION
FIGURE 2: MOUNTING THE GMU 11
Step 4: If necessary, disconnect and discard the F-00013 Static Line Tee-ADAHRS from the F Plastic Tee and F-00014 Static Line
Tee Upsize. See Section 10iS/U and the detail view in Figure 3.
Step 5: Connect the Aft Pitot Line to the F Plastic Tee using the F-00014 as described in Section 10iS/U. If necessary, trim the Aft
Pitot Line as required to prevent interference or chafing on the surrounding structure.
Ensure there are no kinks in the Aft Pitot Line. See Section 10iS/U and the detail view in Figure 3.
FIGURE 3: CONNECTING THE AFT PITOT LINE

42PiS-11RV-12iS001/19/19 PAGE:REVISION:DATE:
VAN'S AIRCRAFT, INC.
Step 1: Remove the F-01206E-1 Baggage Floor Cover, previously installed in Section 38iS/U.
Step 2: Cleco the F-00082 ADAHRS Stiffener to the F-01206E-1. Final-Drill #11 the four holes indicated in Figure 1. Disassemble
and debur.
Step 3: Rivet the F-00082 to the F-01206E-1 as shown in Figure 1. This will form the ADAHRS Baggage Floor Assembly.
FIGURE 1: ADAHRS BAGGAGE FLOOR ASSEMBLY
FIGURE 2: INSTALLING THE ADAHRS
Step 4: Bolt the GSU 25 to the ADAHRS Baggage Floor Assembly as shown in Figure 2.
NOTE: See Section 5.27 for detailed fluid fitting assembly instructions.
Step 5: Install the three FLF-00007 fittings into the "Pitot", "AOA", and "Static" ports of the GSU 25 ADAHRS.
5X LP4-3
3X FLF-00007
4X AN525-10R18 2X NAS1149F0363P
MS21042-3
GSU 25
AFT EDGE OF ADAHRS
BAGGAGE FLOOR ASSEMBLY
AFT EDGE OF
F-01206E-1
F-00082
FINAL-DRILL #11

VAN'S AIRCRAFT, INC.
PAGE: REVISION: DATE: 01/19/190RV-12iS42PiS-12
FIGURE 2: WIRING AND PLUMBING THE GSU 25
GSU 25
15-PIN D-SUB
"ADAHRS"
9-PIN D-SUB
"ADAHRS"
ES-00301
Step 1: Locate an ES-00301 above the lightening hole in the F-01207B-1 Baggage Bulkhead as shown in Figure 1. Match-Drill #30
the F-01207B-1.
Step 2: Rivet the ES-00301 to the F-01207B-1 as shown in Figure 1 and Figure 2, using the hardware called out in Figure 1.
Step 3: Measure and cut the Aft Pitot Line so it extends 24 in. [61.0 cm] forward of the forward-most plastic tie wrap installed in the
F-1280-L Left Side Skin in Section 10iS/U. This is now the F-00216 Garmin Static Line. Keep the remaining PT 1/4 OD Tube.
Step 4: Route the F-00216 forward through the lightening hole in the F-01207B-1 as shown in Figure 2, then insert the end of the
F-00216 into the FLF-00007 in the "Static" port of the GSU 25.
Step 5: Locate the F-00212 Garmin AOA Line (left coiled in the tailcone in Section 42MiS/U).
Step 6: Route the F-00212 forward through the lightening hole in the F-01207B-1 as shown in Figure 2, then insert the end of the
F-00212 into the FLF-00007 in the "AOA" port of the GSU 25.
Step 7: Measure, mark, and cut 103.5 in. [262.9 cm] of the remaining PT 1/4 OD Tube to fabricate the F-00214 Garmin Aft Pitot
line.
Step 8: Route one end of the F-00214 through the lightening hole in the F-01207B-1 as shown in Figure 2, then insert the end of
the F-00214 into the FLF-00007 in the "Pitot" port of the GSU 25.
Note: Ensure all Pitot-Static and AOA Lines are free from debris before connecting them to the
avionics.
ES-00301
F-01207B-1
FIGURE 1: INSTALLING THE PITOT-STATIC LINE SUPPORT
PLASTIC TIE WRAP 8"
Step 9: Loosely secure the F-00212, F-00214, and F-00216 to the ES-00301 using a tie wrap as shown in Figure 2. Leave the tie
wrap loose enough to allow the lines to slide through when the ADAHRS Baggage Floor Assembly is removed.
Step 10: Connect the 15-pin d-sub and 9-pin d-sub connectors labeled "ADAHRS" from the WH-00136 to the GSU 25 as shown in
Figure 2.
Step 11: Loosely secure the wires to the ES-00301 (installed in Section 42MiS/U) using a tie wrap as shown in Figure 2. Leave the
tie wrap loose enough to allow the wires to slide through when the ADAHRS Baggage Floor Assembly is removed.
Step 12: Check for F-00212, F-00214, F-00216, and wire bundle chafing or rubbing on the flight control cables, torque tube, or
surrounding structure. Reinstall the ADAHRS Baggage Floor Assembly as described in Section 38iS/U.
ES-00301 (SECTION 42MiS/U)
PLASTIC TIE WRAP 8"
STATIC
AOA
PITOT
LP4-5
NAS1149FN432P
BAGGAGE
BULKHEAD
ASSEMBLY
F-01207B-1
ADAHRS BAGGAGE
FLOOR ASSEMBLY
FWD
RIGHT
UP
F-00212
F-00214
F-00216

42PiS-13RV-12iS001/19/19 PAGE:REVISION:DATE:
VAN'S AIRCRAFT, INC.
Step 1: Route the F-00214 forward through the fuselage, following the CT-01204 Fuel Cable Assembly through the snap bushings
as shown in Figure 1.
Step 2: Route the forward end of the F-00214 through the center snap bushing in the F-12103 Tunnel Brace as shown in Detail A
in Figure 1. Ensure the F-00214 is free from kinks along its length and does not interfere or chafe against fuel lines, brake lines,
engine and fuel control cables, etc.
The F-00214 will be connected to the FF-1216 Pitot Line later in this section.
Step 3: Loosely secure the F-00212 and F-00214 to the ES-00301s with plastic tie wraps as shown in
Detail B in Figure 1.
PLASTIC TIE WRAP 8"
ES-00301
(SECTION 21iS/U AND 24iS/U)
F-00216
F-00212
F-00214
F-00216
GARMIN STATIC LINE
F-00214
GARMIN PITOT LINE
F-12103
F-00214
MAIN BRAKE LINES
FF-1216
CT-01204
FIGURE 1: ROUTING THE
AIR-DATA LINES DETAIL A
DETAIL B
CT-01204
GSU 25
BAGGAGE BULKHEAD
ASSEMBLY

VAN'S AIRCRAFT, INC.
PAGE: REVISION: DATE: 01/19/190RV-12iS42PiS-14
19X MATCH-DRILL #40 10X MATCH-DRILL #27
IGNORE THIS HOLE
DIMPLE #40 ALL RIVET HOLES
FLUSH THIS SIDE
23X MACH CSK
FLUSH THIS SIDE
FIGURE 1: LOCATING THE F-00063
FIGURE 2: MATCH-DRILLING THE F-01202B-1
FIGURE 3: PREPARING THE F-01202B-1
FIGURE 4: COUNTERSINKING THE F-00063-L
(MIRROR FOR F-00063-R)
Step 1: Cleco the F-00063 Doubler to the aft side of the F-01202B-1 Panel Base flange as shown in Figure 1.
NOTE: Do not match-drill the #27 hole noted in Figure 2 into the F-00063. This hole is not used for the G3X Touch installation.
NOTE: The two upper screw holes in the F-00063 will make notches in the F-01202B-1 flange. See Figures 2 and 3.
Step 2: Match-Drill #27 and #40 all holes not found in the F-01202B-1 using the F-00063 as a guide. See Figure 2.
Step 3: Remove the F-00063 and deburr.
Step 4: Dimple all rivet holes in the F-01202B-1 flange as shown in Figure 3.
Step 5: Machine countersink all rivet holes in the F-00063 as shown in Figure 4. This is now the F-00063-L.
Step 6: Mirror all steps on this page for the right side of the aircraft to fabricate an F-00063-R.
CLECO AS REQUIRED
F-01202B-1 F-00063
F-00063
F-01202B-1
F-01202B-1

42PiS-15RV-12iS001/19/19 PAGE:REVISION:DATE:
VAN'S AIRCRAFT, INC.
IGNORE THIS HOLE
FIGURE 1: INSTALLING THE F-00063-L
(MIRROR FOR RIGHT F-00063-R)
MS21051-L06
2X AN426AD3-3.5
MS21051-L06
2X AN426AD3-4
6X K1000-06
2X AN426AD3-4
AN426AD3-3.5
Step 1: Rivet the F-00063-L and nutplates to the forward side of the F-01202B-1 Panel Base flange as shown in Figure 1.
Step 2: Mirror Step 1 for the right side of the aircraft to rivet the F-00063-R to the F-01202B-1.
F-01202B-1
F-00063

VAN'S AIRCRAFT, INC.
PAGE: REVISION: DATE: 01/19/190RV-12iS42PiS-16
4X
F-00132-R
F-00132-L
FIGURE 1: PREPARING THE F-00132-L & -R
Step 1: Separate the F-00132 Nav/Com Xpndr Firewall Bracket into the F-00132-L &
-R as shown in Figure 1. Note that the F-00132-R has a clearance notch, and the
F-00132-L does not.
Step 2: Machine countersink the nutplate rivet holes in the F-00132-L & -R,
then install the nutplates as shown in Figure 1.
K1000-08
2X AN426AD3-3.5
8X MACH CSK
(FLUSH THIS SIDE)
REMOVE HATCHED AREAS
FIGURE 3: PREPARING THE F-00054-1-L & -1-R
Step 5: Separate the F-00054-1 Inst Stack Angle Nav/Com by
removing the hatched areas shown in Figure 3.
Step 6: Machine countersink the nutplate rivet holes in the
F-00054-1-L & -1-R, then install the nutplates as shown in Figure 3.
6X MS21055-L06
2X AN426AD3-3.5
8X K1000-06
2X AN426AD3-3.5
F-00054-1-R
F-00054-1-L
REMOVE HATCHED AREAS
Step 7: Separate the TOOL-00004 Garmin RV-12iS Drill Templates into the three drill guides by removing the hatched areas
shown in Figure 4.
FIGURE 4: SEPARATING THE DRILL GUIDES
TOOL-00004
F-00132-L DRILL GUIDE
GEA 24 DRILL GUIDE
GAD 29 DRILL GUIDE
REMOVE HATCHED AREAS
FIGURE 2: INSTALLING THE NUTPLATES ON TO
XPNDR BRACKETS
4X K1000-06
2X AN426AD3-3.5
8X MACH CSK
(FLUSH OPPOSITE SIDE)
F-00209
F-00210
Step 3: Machine countersink the nutplate rivet holes in the F-00209 Nav/Com Xpndr Bracket Right and F-00210 Nav/Com
Xpndr Bracket Left as shown in Figure 2.
Step 4: Install the nutplates onto the F-00209 and F-00210 as shown in Figure 2.
(CLEARANCE NOTCH)

42PiS-17RV-12iS001/19/19 PAGE:REVISION:DATE:
VAN'S AIRCRAFT, INC.
CLECO
MATCH-DRILL #30
FIGURE 1: PREPARING THE F-01201A-1
NOTE: Check both sides of the firewall for clearance before match-drilling holes to prevent
inadvertent damage.
Step 1: Temporarily remove the Rotax Fuse Box from the forward side of the F-01201A-1 Firewall Top. See
Section 46iS.
Step 2: Temporarily attach the GEA 24 Drill Guide and the F-00132-L Drill Guide to the
F-01201A-1 using screws as shown in Figure 1.
Step 3: Remove the three rivets that will interfere with the F-00132-R. See Figure 1.
Step 4: Cleco the F-00132-R to the F-01201A-1 as shown in Figure 1.
Step 5: Match-drill #30 the holes in the F-00132-R
and the F-00132-L Drill Guide as shown in Figure 1.
Step 6: Match-drill #11 the holes in the
GEA 24 Drill Guide as shown in Figure 1.
Step 7: Remove the F-00132-R and both
drill guides. Discard the two drill guides, but keep
the screws, washers, and nuts.
Step 8: Debur the F-00132-R and
F-01201A-1.
Step 9: Make two ES-000334 Harness
Sheaths from EA HOSE H151 as shown in
Figure 2.
F-00132-R
MATCH-DRILL #30
MATCH-DRILL #30
F-01201A-1
REMOVE EXISTING
RIVETS
3X TEMPORARY #8 SCREWS
F-00132-L DRILL GUIDE
MATCH-DRILL #30
4X TEMPORARY #10 SCREWS
GEA 24 DRILL GUIDE
MATCH-DRILL #11
(CLEARANCE NOTCH)
FIGURE 2: FABRICATING THE ES-00334
EA HOSE H151
SLIT ENTIRE LENGTH,
ONE SIDE

VAN'S AIRCRAFT, INC.
PAGE: REVISION: DATE: 01/19/190RV-12iS42PiS-18
AN525-832R6
NAS1149FN832P
MS21042-08 3X
2X SB1250-16
(ROUTE WIRES
THROUGH BUSHINGS)
13X LP4-3
F-00130-L
F-00130-R F-00054-1-R
F-00054-1-L
F-01201A-1
F-01202B-1
FF-1216
SB750-10
NOTE: Refer to Figure 1 for all steps on this page.
Step 1: Rivet the F-00130-L & -R GTN 650 Support Bracket and the F-00054-1-L & -1-R to the F-01202B-1, placing the manufactured rivet heads below the F-01202B-1.
Step 2: Rivet the F-00132-L & -R to the F-01201A-1, placing the manufactured rivet heads on the forward side of the F-01201A-1.
Step 3: Install the screws, nuts, and washers as shown. These fasteners fill holes in the F-01201A-1 not used for the Garmin installation.
Step 4: On the forward side of the firewall only, cover the end of each rivet and screw with a thin layer of fuel tank sealant.
Step 5: Route the WH-00136 main wire harness branches through the slotted holes in the F-00130-L & -R.
Step 6: Split the snap bushings, then place the snap bushings over each branch of the WH-00136.
Secure the snap bushings in the F-00130-L & -R as shown.
Step 7: Install the snap bushing in the F-00130-L then route the FF-1216 Pitot Line
(installed in Section 47iS/U) through the snap bushing as shown and through the wire pass
through in the F-01202B-1. F-01202B-1s with dual pass through's may use either for the
FF-1216.
Step 8: Wrap one ES-00334 around each branch of the WH-00136 just inboard of the
F-00130-R & -L.
Place the ES-00334s against
the inboard face of the snap
bushings, then use two
tie-wraps to secure each
ES-00334 onto the harness.
See Figure 1 and Detail A.
FIGURE 1: INSTALLING THE AVIONICS BRACKETS
F-00132-L
F-00132-R
2X
WH-00136
(RIGHT BRANCH
SHOWN)
10X LP4-3
DETAIL A
2X ES-00334
AUTOPILOT
AND BATT
WIRES
GARMIN GTN 650
MOUNTING RACK
(INSTALLED ON
NEXT PAGE)
WH-00136
F-01202B-1
ES-00334
2X PLASTIC TIE-WRAP 5.5"
(MIRROR FOR LEFT SIDE) DETAIL A

42PiS-19RV-12iS001/19/19 PAGE:REVISION:DATE:
VAN'S AIRCRAFT, INC.
AN507-632R6
NAS1149FN632P
MS21042-06
8X
F-00209
F-00210
4X AN525-832R8
FIGURE 1: GARMIN GTN 650 BACKPLATE
P1002
(NOT USED) CONNECT
"GPS" TNC
CONNECT
"COM" BNC
CONNECT
"NAV" BNC
INSTALL "P1001" CONNECTOR
INSTALL "P1003" CONNECTOR
INSTALL "P1004" CONNECTOR
F-00054-R-1
F-00054-L-1
F-00130-L
F-00132-L
F-00132-R
FIGURE 2: INSTALLING GTN
650 MOUNTING RACK
NOTE: The COM, NAV, and GPS coax cables use solid-core conductors which are prone to overstraining. They should
be the last cables connected to the GTN 650 Backplate, and should not be kinked or bent tighter than 1 in. [25.4 mm]
radius.
Step 1: Assemble the Garmin GTN 650 backplate with the included hardware as shown in Figure 1 and the Garmin GTN 650
Installation Manual.
Install the "P1001", "P1003", and "P1004" connectors (part of the WH-00136) on to the backplate.
Connect the "COM", "NAV", and "GPS" Coaxial cables (part of the WH-00136) to the respective connectors on the backplate.
Step 2: Install the Garmin GTN 650 mounting rack on to the Garmin GTN 650 backplate as shown in the in Garmin GTN 650
Installation Manual.
NOTE: While positioning the Garmin GTN 650 backplate and mounting rack for final
installation, check that no wires or cables are being overstrained or kinked. Adjust the
placement or exact routing of the wires and cables if necessary.
Step 3: Secure the F-00209, F-00210, and Garmin
GTN 650 mounting rack to the F-00130 -L & -R, the
F-00132-L & -R, and the F-00054-1-L & -1-R as shown
in Figure 2.
Step 4: Ensure that the wires of the left
and right branches of the WH-00136
are protected by the ES-00334, and
will not chafe on the sheet metal
edges of the Garmin GTN 650
backplate or mounting rack.
Adjust harness positioning
as necessary.
GARMIN GTN 650 MOUNTING RACK

VAN'S AIRCRAFT, INC.
PAGE: REVISION: DATE: 01/19/190RV-12iS42PiS-20
GTX 35R RACK
4X AN507-632R6
AN507-632R6
NAS1149FN632P
MS21042-06
6X
Step 1: Assemble the Garmin GMA 245 backplate and the d-sub connectors labeled "J2401" and "J2402" from the WH-00136 as
shown in the GMA 245 Installation Manual and Figure 1.
Step 2: Install the Garmin GMA 245 backplate in the GMA245 mounting rack as shown in the GMA 245 Installation Manual and
Figure 1.
Step 3: Fasten the GMA 245 mounting rack to the F-00054-1-L & -1-R, the F-00209, and the F-00210 as shown in Figure 1.
Step 4: Install the GTX 35R Rack as shown in Figure 1.
"J2401"
CONNECTOR
"J2402"
CONNECTOR
GMA 245 MOUNTING RACK
GMA 245 BACKPLATE
F-00054-1-R
F-00054-1-L
F-00210
F-00209
FIGURE 1: INSTALLING THE GMA 245 AND GTX 35R RACKS